Space Shuttle Aerodynamic Development Studies

Aerodynamic studies have been directed to investigating the design requirements associated with the unique operational flight profile of the space shuttle system. The flight regimes include launch; stage separation, orbital operations, entry, transition, cruise and landing. Aerodynamic configurations have been developed by interpreting the mission requirements in terms of required or desired aerodynamic characteristics. Analyses of configuration effects have been performed to obtain these characteristics. In many cases, experimental data has been obtained to either substantiate analytic trends or to provide basic data where the problem is not amenable to analysis

Space Shuttle Booster Wing Geometry Trade Studies

The subsonic aircraft mode of a Space Shuttle booster establishes design requirements on airbreathing engine size and flyback fuel allotment. Trade study results show the influence of wing geometry variations on the flyback systems weight (wing, jet engine and flyback fuel weight) of a canard Space Shuttle booster. The influence of such wing geometry parameters as aspect ratio and wing area is discussed. Wing weight trends with wing geometry, obtained from conventional cargo, bomber and fighter airplane weight histories, are correlated with predicted values for Space Shuttle wings where structural span, load factor, and other design parameters are taken into account. For other than cruise performance reasons, a lower limit of wing area is defined; the influence of other phases of the booster mission profile, including launch, entry, and landing is presented. Aspect ratio, however, is influenced primarily by cruise performance and cost considerations. The influence of ground rules, such as choice of flyback fuel, headwind profile, and required range is discussed